Attachment 1 Composite Panels Specification Sheet.pdf

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FY25 Composite Training Panels
Solicitation number
FA302025Q0002
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This document is a Specifications Sheet for the manufacture of Composite Training Panels, which are used by the Air Force for their Supplemental Advanced Composite Repair course. The panels have specific requirements for the exterior skin, fiberglass/phenolic honeycomb core, and interior Kevlar 49 aramid prepreg skin. The related federal contract opportunity is a Request for Quotes (RFQ) to provide these Composite Training Panels to NAS Pensacola, FL. The solicitation, #FA302025Q0002, is a total set-aside for small business concerns under NAICS code 325211. Quotes are due by 1:00 PM CST on Monday, December 2, 2024, and all questions must be submitted by 1:00 PM CST on Tuesday, November 26, 2024. The Government anticipates awarding a single Firm Fixed Price (FFP) contract.

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FY25 Composite Training Panels Combo.pdf PDF
FY25 Composite Training Panels Combo.pdf PDF
Attachment 2 - FA302025Q0002 Provisions and Clauses.pdf PDF

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SPECIFICATIONS FOR MANUFACTURE OF COMPOSITE TRAINING PANELS, Panel Composite, Panel part number/NSN: 9390-CO-MPO-SITE

(Panels are used by ASM, Supplemental Advanced Composite Repair course)

See Notes I - 4 for materials requirements. Panel overall width and length dimensions +/- .125 tolerances.

I. Exterior skin 8 Plies, quasi-isotropic lay-up unidirectional graphite epoxy tape, Hexcel number T2C- 190-12-F263-2, or equal to (Boeing Material Specification) BMSS-212 TY3 CL! GR190. Balanced ply orientation [(+45 / -45 / 0 / 90)] [(90 / 0 / -45 / +45)]

2. Fiberglass/ Phenolic honeycomb core, 3/16-4.0, 1" thick HRP, (height I" continuous, with no splices or butts) HRP-3/16-4.0. Transition angles to be uniform.

3. Interior skin Kevlar 49 Aramid prepreg. Cytec number MXM-7880-/285, or equal to BMSS-218 ST285, 4 plies ( crowfoot) cross ply lay-up.

4. Internal and external skins to core, bond with film adhesive equivalent to BMS5-154 TY2 CL! GR5.

NOTE: All surfaces must be wrinkle free with no seams or butted joints.

18"

2 1/211 ....._ 1 11----Jiitr

1,4" Radius

Interior Skin Side Kevlar 49 Aramid Prepreg

14 1/2" 18"

Note 3

Note2 u.--- Note 1

:I Specification sheet/drawing for all specific design requirements.

Advanced composite training panel, composite FFP-Panel, Composite l" thick core XIS" XI 8".

Side 1 (exterior Skin), 8 plies BMS8-212 TY3 CL! GR 190 equivalent, balanced ply lay-up, {[(+45, -45, 0, 90)][(90, 0, -45, +45)]} Fiberglass/Phenolic Honeycomb Core 3/16-4.0, 1.0" Thick HRP.

Side 2, (Interior Skin) is Kevlar 49 aramid prepreg. Equal to Boemg spec BMSS-218 ST285, 4 plies ( crowfoot weave) cross ply lay-up. 2 sides with transition edges as per specification sheet with W' radiuses;

core height continuous, with no splices or butts. Skin to core bond with film adhesive equivalent to BMSS-

154 TY2 CL! GR5

File details come from the government source that posted it. Updated .